Multi-component multi-satellite network

ABSTRACT

Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

CROSS REFERENCE TO RELATED APPLICATIONS

This Patent Application is an application claiming priority under 35U.S.C. §§ 111(a) and 365(a) to PCT/162021/060284, entitled “DEVICES,SYSTEMS AND METHODS FOR AUGMENTING SATELLITES,” filed Nov. 5, 2021,which is related to and claims priority under 35 U.S.C. § 119(e) to U.S.Provisional Patent Application No. 63/198,692, entitled “NOVEL METHOD TOAUGMENT EXISTING SATELLITES WITH SITUATIONAL AWARENESS SENSINGCAPABILITY,” filed Nov. 5, 2020, which is incorporated by reference inits entirety for all purposes.

FIELD OF THE INVENTION

The invention relates to the augmentation of satellites, for example, byproviding an enhancement module that adds a capability to the satellite,modifies the function of the satellite, and/or extends the function ofthe satellite.

BACKGROUND

Satellite operations have remained essentially unchanged since 1957 whenthe first manmade object was launched into orbit. With the exception ofthe Hubble Space Telescope and the International Space Station, both ofwhich required manned missions to service, satellites are launched witha certain level of hardware technology capability which does not changethroughout the duration of the satellite's mission. Due to the longlifespans necessitated by the large, combined asset and launch costs,the result is outdated technology in space assets long before their endof life. In other words, while the rate of technological advancement isexponentially increasing, the traditional method of satellitedevelopment and operation has not been able to maintain this same pacedue to the unit economics and cost of space access. As a result,technology on orbit significantly lags terrestrial capabilities onaverage and at any given point in time.

In this regard, satellite-based business models are bottlenecked by thecurrent mode of satellite operations causing new, innovative businessmodels to be economically infeasible. This is caused by two primaryreasons—satellite operations and satellite design. As it relates to thetraditional satellite design process, satellites are typically producedas a one-off design or a series of similar designs discretely designedto serve one specific set of mission objectives.

While some base-level design decisions and components, such as the mainbus, can be used across several different missions and satellitedesigns, the general industry process is to redesign and produce a new,specific solution to serve a certain purpose, even if much of thecomponentry is similar across missions. A different set of missionobjectives or different payload technology will often necessitate aredesign of several subsystems, if not the entire satellite. This methodof designing and integrating satellites is costly and skilled-laborintensive, and the resulting product is not assembled in a manner thatcan be easily taken apart for servicing or repair on the ground by theskilled technicians that built the satellite, let alone on-orbit by ageneral servicing satellite.

Moreover, due to high asset cost and necessary long lifespan for fullasset depreciation and return on investment under the current systems ofsatellite operations, the technology in orbit at any discrete point intime significantly lags the technology available terrestrially. Thenature of these systems results in a relatively static commercial (andgovernmental) technological space marketplace as expansion into dynamicmarketspaces with changing customer behavior is effectively infeasibledue to financial considerations.

Thus, systems are currently in development along the lines of limitedin-orbit repair and small lifetime extensions. However, both are problemmitigations, not solutions, due to the static nature of the valueproviding technology contained by the satellite.

Moreover, there is little technology that addresses incorporatingregularly planned, autonomous or semi-autonomous in-orbit hardwareexchanges to increase the capabilities of space assets such assatellites, thereby enabling longer lifespan for satellites and similarspace assets and which ultimately allow for new business models to beexplored by satellite operators as the hardware limitations imposed bylaunching a static technology level are removed.

Additionally, geosynchronous and/or geostationary orbits (GEO) providesignificant benefit to humanity and continue to be used in high-value,high-need economic ventures as well as significantly valuable scientificendeavors. However, while collisions between space assets or collisionsbetween space assets and orbital debris within GEO have been thought tobe relatively rare, low-probability occurrences, recent literaturepublished in 2018 entitled: “A comprehensive assessment of collisionlikelihood in Geosynchronous Earth Orbit” suggests that the probabilityof collision may be significantly higher—on the order of one expectedcollision every four years between an active GEO satellite and an objectlarger than one centimeter.

Additionally, the relative velocities during collisions are likely to besubstantially higher than previously expected due to objects in highlyeccentric orbits crossing the GEO belt. These risks are compounded bythe fact that ground-based sensing capability to the GEO belt is limitedto detection of objects roughly greater than one meter in diameter,making much of the debris posing significant risk to high-economic valuespace assets undetectable. These routine collisions that have goneunnoticed and untracked to date are theorized to be potential causes ina number of undiagnosed GEO satellite losses.

This risk of collision combined with the extreme economic value of theGEO belt and the long-term cost of any number of collisions betweenobjects in the GEO belt necessitate higher-fidelity space situationalawareness technology for satellites occupying the GEO belt. Byaugmenting traditionally ground-based satellite collision avoidanceoperations with data collected in-situ, higher confidence collisionavoidance becomes possible by making the satellite(s) at risk ofcollision active participants in the collision avoidance algorithm.

Thus, systems and methods that provide for the augmentation ofsatellites, for example, by providing an enhancement module that adds acapability to the satellite, modifies the function of the satellite,and/or extends the function of the in satellite are desirable.

SUMMARY

The present disclosure provides devices, systems and methods for anin-orbit, retrofittable satellite system for an in-orbit host satellitecomprising an enhancement module for adding a capability to the in-orbithost satellite, modifying the function of the in-orbit host satellite,and/or extending the function of the in-orbit host satellite. Thein-orbit, retrofittable satellite system further comprises a transfervehicle for transferring the enhancement module from a first location toa second location and a service vehicle for receiving the enhancementmodule from the transfer vehicle and installing the enhancement moduleon the in-orbit host satellite. The in-orbit, retrofittable satellitesystem may further comprise multiple enhancement modules.

The present disclosure further comprises devices, systems and methodsfor an in-orbit space situational awareness system. The term “spacedomain awareness” is sometimes used as an equivalent of spacesituational awareness, though for convenience of reference, “spacesituational awareness” is used herein. In-orbit space situationalawareness systems in accordance with the present disclosure comprise oneor more in-orbit host satellites having one or more space situationalawareness enhancement modules attached thereto, the space situationalawareness enhancement module comprising sensors such as satellitespatial location/position sensors, range sensors, navigation sensors,and/or proximity sensors for detecting other objects in-orbit, theirlocation, speed, acceleration, orbital trajectory or the like, whereinthe space situational awareness enhancement modules communicate tocreate an in-orbit mesh network between the in-orbit host satellites.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings provide a further understanding of theinvention and are incorporated in and constitute a part of thisspecification, illustrate embodiments of the invention, and togetherwith the description serve to explain the principles of the invention.

FIG. 1 is an illustration of a transfer vehicle, a service vehicle, ahost satellite and an enhancement module of a retrofittable satellitesystem in accordance with the present disclosure;

FIG. 2 is a perspective view of the top of an enhancement module with aconnector port used to interface with the service vehicle;

FIG. 3 is a perspective view of a host satellite with multipleenhancement modules attached thereto in accordance with the presentdisclosure;

FIG. 4 is a perspective partial view of a host satellite illustratingmultiple attachment mechanisms in accordance with the presentdisclosure;

FIG. 5 is a close-up perspective view of an attachment mechanism on ahost satellite configured as bin for receiving an enhancement module inaccordance with the present disclosure;

FIG. 6 is a perspective view of the bottom of an enhancement module withmultiple attachment mechanisms in accordance with the presentdisclosure;

FIG. 7 is a perspective view of an enhancement module relative to astandard basketball in accordance with the present disclosure; and

FIG. 8 is an illustration of the earth orbited by a number of hostsatellites with space situational awareness enhancement modules attachedthereto in accordance with the present disclosure.

DETAILED DESCRIPTION

Persons skilled in the art will readily appreciate that various aspectsof the present invention may be realized by any number of methods andapparatuses configured to perform the intended functions. Stateddifferently, other methods and apparatuses may be incorporated herein toperform the intended functions. It should also be noted that theaccompanying drawing figures referred to herein are not all drawn toscale but may be exaggerated to illustrate various aspects of thepresent invention, and in that regard, the drawing figures should not beconstrued as limiting. Finally, although the present invention may bedescribed in connection with various principles and beliefs, the presentinvention should not be bound by theory.

The above being noted and as will be described in more detail below, thepresent disclosure contemplates devices, systems and methods for anin-orbit, retrofittable satellite system for in-orbit host satellitescomprising enhancement modules for adding one or more capabilities toin-orbit host satellite, modifying the function of the in-orbit hostsatellite, and/or extending the functions of in-orbit host satellites.The present disclosure further comprises devices, systems and methodsfor an in-orbit space situational awareness system, comprising one ormore in-orbit host satellites having one or more space situationalawareness enhancement modules attached thereto, the space situationalawareness enhancement module comprising sensors such as satellitespatial location/position sensors, range sensor, navigation sensors,and/or proximity sensors for detecting other objects in-orbit, theirlocation, speed, acceleration, orbital trajectory or the like, whereinthe space situational awareness enhancement modules communicate tocreate a decentralized, in-orbit, mesh positioning, ranging, navigationand/or proximity network between the in-orbit host satellites. Suchnetworks allow for benefits such as mitigation of collision risk, aswell as the creation of high-fidelity simulations of the GEO belt debrisas debris encounters and characteristics can be collected and verifiedby in-situ sensing capability.

For example, in accordance with the present disclosure, an in-orbitretrofittable satellite system allows an in-orbit host satellite (orsimply, “host satellite”) to be retrofitted with a module for changingthe capability and/or functional operability of the host satellite. Inthis regard, “retrofit” or “retrofittable” refers to the addition of anew device (i.e., a “module” or “enhancement module”) to an originaldevice (i.e., a satellite) that was not available, necessary, or presentwhen the original device was manufactured. In the context of the presentdisclosure, the enhancement module is retrofit to the host satellite toadd capabilities to or otherwise modify a function of the hostsatellite, including those described hereinbelow. The enhancementmodules may also extend a capability or function of the host satellite.In accordance with various alternative aspects of the presentdisclosure, enhancement modules may be attached to host satellites onearth and/or prior to being placed in orbit.

In accordance with the present disclosure, with reference to FIG. 1 ,the retrofittable satellite system may comprise a transfer vehicle 110for transferring the enhancement module 120 from a first location to asecond location. For example, the first location may be earth or amodule transport spacecraft and the second location may be a locationproximate a service vehicle 130. The service vehicle 130 receives themodule 120 from the transfer vehicle 110 and takes the module 120 to ahost satellite 100 for attachment or installation on the host satellite100. In accordance with some aspects of the present disclosure, thetransfer vehicle 110 and the service vehicle 120 may be the samevehicle, such that it both transfers the module 120 from the firstlocation (e.g., earth or a spacecraft) to the host satellite 100 (thesecond location), where in turn it adds or removes modules 120 to thehost satellite 100 (as described herein).

In accordance with the present disclosure, in addition to the attachmentor installation of modules 120 host satellites 100, the service vehicle120 may also remove modules 120 and other components from hostsatellites 100, for example, for replacement with new modules 120 withnew or different capabilities or with the same, for example, to extendthe life of the mission of the host satellite 100.

In accordance with the present disclosure, with reference to FIG. 2 ,the enhancement module 120 may include one or more female connectorports 195 used as an interface for communication between the servicevehicle 130 and the host satellite 100 for example, during installationor removal of enhancement modules and other similar processes.

In accordance with the present disclosure, the module 120 may simply beattached (as described below) to the host satellite 100 and operateindependently of the functionality of the host satellite 100, though inother applications, the module 120 may be functionally installed on thehost satellite 100 such that it communicates and operates with theexisting functionality of the host satellite 100. Additionally, inaccordance with various aspects of the present disclosure, the transportvehicle 110 may carry multiple modules 120 of similar or varyingcapabilities, and the service vehicle 130 may install multiple modules120 on one or more host satellites (e.g., as shown FIG. 3 ).

In accordance with the present disclosure, with reference to FIG. 4 ,the host satellite 100 may have one or more attachment mechanisms 150for receiving the enhancement module 120. For example, with reference toFIG. 5 , a close up view of an attachment mechanism 150 configured asbin having a raised perimeter 170 with an aperture 180 configured with aprofile similar to the module 120 itself so as to “snugly” receive themodule 120 therein and may further include additional attachment and/ormodule 120 and host satellite 100 communication means such thosedisclosed below.

In accordance with alternative aspects of the present disclosure, thebin-style attachment mechanisms 150 may be reversed in orientationbetween the modules 120 and the host satellite. In other words, the hostsatellite 100 may include a host projection (not shown) extending fromthe surface of the host satellite and the module 120 may include anaperture that receives the projection from the host satellite tofacilitate connection therebetween.

The attachment mechanism(s) 150 facilitates the connection of the module120 to the host satellite. In accordance with various aspects of thepresent disclosure, the attachment mechanism 150 may simply provide asecure mounting point with no interface or communication (i.e., withcontrol system, power supply, or the like) between the module 120 andthe host satellite 100. For example, non-limiting examples of attachmentmechanisms 150 may include means for securing the module 120 to the hostsatellite, often, though not necessarily, on a general flat surface ofthe host satellite 100, including base plates, synthetic setae,adhesives, welding, magnets bolts, screws and the like. With briefreference to FIG. 6 , four “panels” 185 on enhancement module 120illustrate the possible placement and location of such synthetic setae,adhesives, base plates, or magnets, though other shapes, configurationsand numbers of panels may be substituted and still fall within the scopeof the present disclosure.

In accordance with various additional (or alternative) aspects of thepresent disclosure, the enhancement modules 120 may attach to the hostsatellite 100 via any known or as yet known mechanism, such as, forexample, rivets, screws, hot-melt compounds, mechanical clamps or otherhard point attachment mechanisms, Van Der Waals forces, electrostaticadhesion, and other methods of adhesion similar to tape.

In accordance with other aspects of the present disclosure, theattachment mechanism 150 may provide communication between the hostsatellite 100 and the enhancement module 120. Communication may includeelectronic, optical or other one or two-way communication with hostsatellite components related to control systems, power supplies,processing systems, and the like. For example, additional communicationoptions may include inter-module communication on a single hostsatellite 100 via electromagnetic radiation, wired data connection ofelectrical or optical type or other possible physical, wired or wirelesscommunication types; modules containing one or more sensors suitedspecifically to, but not limited to rendezvous and proximity operationswith communication enabling low-latency data-transfer to assist inrendezvous and proximity operation maneuvers between one or moreparticipating satellites; enhancement modules 120 containing one or moresensors suited specifically to, but not limited to impact avoidance andor close proximity satellite detection, and or close proximity satelliteidentification; enhancement modules 120 that contain and are capable ofdeploying countermeasures in response to a perceived threat; andenhancement modules 120 that use the Tracking and Data Relay Satellite(TDRS) Systems for communication with other enhancement modules 120 andor ground stations.

With reference back to FIGS. 4 and 5 and the bin-style attachmentmechanisms 150, the bins may include bin-module interface connectors(not shown) and the enhancement module 120 may include module-bininterface connectors (not shown), wherein an enhancement moduleprojection or the enhancement module 120 itself is inserted into the binsuch that the bin-module interface connectors and the module-bininterface connectors connect to form a bin-enhancement modulecombination, with the above-noted communication therebetween.

In accordance with other aspects of the present disclosure, thebin-module interface connectors and the module-bin interface connectorsmay include any now known or as yet unknown method of connecting tocomponents that must communicate with one another, such as through maleand female pin connectors, androgenous pin connectors, opticalconnectors, NFC, Bluetooth, IR, RF and the like.

In accordance with other aspects of the present disclosure, enhancementmodules 120 may be configured in any desirable size, shape and/orgeometry depending on the particular application. For example, withreference to FIG. 7 , enhancement modules 120 may be slightly largerthan a standard basketball 125 thus facilitating the enhancement modules120 and/or the attachment mechanisms 150 to be attached to any number oflocations on a host satellite, depending on the application, though inaccordance with various aspects of the present disclosure, because oftheir larger areas of the radiator panels 160 relative to the size ofthe body of most satellites, as illustrated in FIG. 1 , the enhancementmodules 120 and/or attachment mechanisms 150 may be attached to radiatorpanels 160 on the host satellites 100.

In accordance with the present disclosure, enhancement modules 120provide any number of increased or enhanced capabilities, such as spacesituational awareness capabilities, including for example, space trafficmanagement, local space awareness, orbital data and various otherinformation related to the space surrounding the host satellite 100 towhich the enhancement module 120 is attached. Enhancement modules 120 inaccordance with the present disclosure may also allow “missionextension” capabilities. For example, older host satellites 100 that benearing the end of their functional relevance of capabilities may haveenhancement modules 120 retrofitted to them to provide new capabilitiesor improve or extend the life of old capabilities, such earth to orbitsatellite communications, GPS, optical and radio telescopic, etc. Theenhancement modules 120 may also provide the ability to add power to thehost satellites 100 and/or reposition host satellites 100 that arelosing or have lost the ability to reposition (if they ever had theability).

In accordance with various aspects of the present disclosure, theenhancement modules 120 may also provide the ability for enhancementmodules 120 to communicate with one another on the same host satellite100, different host satellites 100, or both, which in turn can add newcapabilities related to the various space awareness functionalitiesmentioned above and described in more detail hereinbelow.

In accordance with various aspects of the present disclosure and withreference to FIGS. 2, 6 and 7 , various components that may be includedin enhancement modules 120 are illustrated. For example, in accordancewith various aspects of the present disclosure, a variety ofconventional satellite components, now known or as yet unknown, may beincluded with the enhancement modules, including but not limited to:

-   -   onboard processors (which may include FPGA logic gates);    -   power generation components such as one or more solar panels;    -   power storage components such as one or more batteries;    -   one or more power distribution units;    -   one or more optical sensor systems (for example, one or more        cameras); and    -   communication arrays (for near and/or far communication).

In accordance with the present disclosure, the retrofittable satellitesystem may provide an in-orbit space situational awareness systemthrough enhancement modules 120 attached to host satellites. Forexample, with reference to FIG. 8 , a first in-orbit host satellite 101having a space situational awareness enhancement module 120 attachedthereto, the space situational awareness enhancement module comprisingsensors such as satellite spatial location/position sensors, rangesensor, navigation sensors, and/or proximity sensors for detecting otherobjects in-orbit, their location, speed, acceleration, orbitaltrajectory or the like.

In accordance with the present disclosure, one or more space situationalawareness enhancement modules 120 may be attached to the first in-orbithost satellite 101 without a direct interface with any power, processingor control systems of the first in-orbit host satellite 101, though inaccordance with other aspects, the space situational awarenessenhancement module 120 may have a direct interface with power,processing or control systems of the first in-orbit host satellite 101.

In accordance with the present disclosure, the space situationalawareness enhancement module 120 may use electro-optical, RADAR, LIDAR,IR, RF or the like to determine space object information related tocharacteristics such as relative size, geometry, and/or anidentification of other space objects in-orbit.

In accordance with the present disclosure, the space situationalawareness enhancement module 120 on the first in-orbit host satellite101 transmits the space object information to a ground-based spacesituational awareness system for processing the space object informationfor purposes such as those described hereinbelow.

In accordance with the various alternative aspects of the presentdisclosure, the in-orbit space situational awareness system may comprisea “hub-and-spoke” space situational awareness mesh network furthercomprising one or more additional space situational awarenessenhancement modules 120 attached to at least one additional in-orbithost satellite 101 a, 101 b that transmits additional object informationto the ground-based space situational awareness system.

In accordance with the various alternative aspects of the presentdisclosure, the space situational awareness enhancement modules 120 maycommunicate with space assets including additional in-orbit hostsatellites 101 a, 101 b, which in turn creates an in-orbit mesh networkbetween the in-orbit host satellites.

In accordance with the various alternative aspects of the presentdisclosure, the space situational awareness enhancement modules 120 mayalso or alternatively communicate with space assets other than in-orbithost satellites 101 a, 101 b such as other space craft, non-hostsatellites and/or other intermediary systems such as ground basedsystems and other intermediary space situational awareness systems tocreate an in-orbit mesh network.

In accordance with the present disclosure, one or more of the in-orbithost satellites 101, 101 a, 101 b are configured to change trajectorybased on input from the hub-and-spoke space situational awareness meshnetwork.

Thus, in-orbit space situational awareness systems in accordance withthe present disclosure provide for the ability of the space situationalawareness enhancement modules 120 to be placed in a manner thatmaximizes the statistical likelihood of detection of threatening objectsin potentially intersecting trajectories based on orbital parameters andrisk characteristics of the mission. For example, the cluster nature ofthe modules 120 can be used to optimize system behavior.

Additionally, if there is no line-of-sight between space situationalawareness enhancement modules 120 attached to the same host satellite100, communication between the modules 120 can be accomplished via anacoustic-mechanical schema targeting the resonant frequency range of thelaunch vehicle for the host satellite 100 to minimize interference andvibration effects felt by sensitive electronics within the hostsatellite.

Additionally, communication between space situational awarenessenhancement modules 120 on the same host satellite 100 may beaccomplished by any other means of wired or wireless communicationincluding but not limited to wired electric, wired optical, wirelessoptical, electromagnetic, wireless electromagnetic, and other known oras yet unknown methods of producing module to module communication.

In the event an enhancement module that is acting as a transmissionrelay for a second enhancement module in the chain to communicate with athird enhancement module loses pass-through communication capability orotherwise becomes non-responsive, a passive communication relay methodmay be utilized comprising a fixed length of fiber-optic or otherwaveguide of variable shape along its length to passively passelectromagnetic radiation to the third enhancement module from thesecond enhancement module without the need for communication andinteraction from the second enhancement module. Additionally, a similareffect can be accomplished using mirrors, flat reflectors, refractors,waveguides and/or repeaters depending on the orientation of enhancementmodules and communication schema. Further still, the signal acquired bythe passive routing mechanism may be split to communicate with more thanone enhancement module at a time using a single signal.

In accordance with various aspects of the present disclosure,inter-module communication within the bounds of the same host satellite100 may allow for “cluster” behavior to drive the communication andinteraction schema with other enhancement modules 120 besides theenhancement modules 120 on the same host satellite 100. This clusteringbehavior allows for risk reduction of the severity of any single modulefailure.

In accordance with various aspects of the present disclosure,enhancement modules 120 on different host satellites 100 may communicatebetween each other in a manner similar to other space assets, usingvarying frequencies of electromagnetic radiation or any othermethodology chosen to be appropriate including optical LASER systems.Similarly, the enhancement modules 120 may communicate with other spaceassets or directly to ground stations using varying frequencies ofelectromagnetic radiation or any other methodology chosen to beappropriate including optical LASER systems.

Enhancement modules 120 may use ground stations or other space assets asa relay when communicating between modules on different host satellites.In the event multiple modules 120 are attached to a single hostsatellite 100, the most optimal module attached to the host satellite100 may be dynamically chosen as the “clusterhead” to communicate toother enhancement modules 120 besides the enhancement modules 120 on thesame host satellite 100 based on orientation, power, bandwidth and/orother heath monitoring and/or performance metrics.

In accordance with various aspects of the present disclosure, designatedcommunication roles can shift between enhancement modules 120 dependingon desired outcomes of the mission and the additional external actors.This switching behavior can be tailored to optimize resource use basedon the cluster nature mechanics of the enhancement module groups,including transitioning into separate colonies in the event of anirrecoverable cluster communication link failure. In the event more thanone host satellite 100 is in near proximity, the enhancement modules 120can communicate within a single host satellite 100 to the optimalenhancement module 120 and this optimal enhancement module 120 can thencommunicate directly with an optimal enhancement module 120 on anotherhost satellite 100. The optimal enhancement module 120 on the secondhost satellite 100 may then communicate directly to a ground station oranother space asset or it may communicate inside its host group ofenhancement modules 120 to another optimal enhancement module 120 forcommunication to a ground station or another space asset.

In accordance with another aspect of the present disclosure, anotherimplementation of enhancement modules for increased space situationalawareness related to positioning, ranging, navigation and proximitysensing comprises all the above description, as well as including thedistinction of separable base units and top units within a singleenhancement module 120. For example, with reference to FIG. 6 , the baseunit comprises the mechanical attachment mechanisms 150 to the hostsatellite 100, a structure to support the top unit and anotherattachment mechanism to the top unit. The top unit houses the varioushardware contemplated herein and structure to support and protect thehardware and the attachment mechanism 150 to the base unit.

In accordance with another aspect of the present disclosure, anotherimplementation of enhancement modules for increased space situationalawareness related to positioning, ranging, navigation and proximitysensing comprises all the above description, as well as including theaddition of an interface port between at least one of the enhancementmodules 120 and the host satellite 100 for use of the host satellite 100communications and data subsystem. Additional enhancement modules 120 onthe same host satellite 100 may communicate with a docked module 120using wired or wireless communication including but not limited to wiredelectric, wired optical, wireless optical, electromagnetic, wirelesselectromagnetic, and other known or as yet unknown methods of producingmodule to module communication.

Additionally, the docked module 120 may use host satellite 100 powersystem instead of being isolated from the host satellite. The attachmentmechanism 150 may be direct to a custom or pre-existing port on the hostsatellite 100 or it may be through a pass-through device such as arouting node or other switchable device present at launch or added afterlaunch.

Finally, it will be apparent to those skilled in the art that variousmodifications and variations can be made in the present inventionwithout departing from the spirit or scope of the invention. Forexample, numerous materials, shapes, sizes and configurations can besubstituted in place of those described herein. Thus, the presentdisclosure covers the modifications and variations provided they comewithin the scope of the appended claims and their equivalents.

We claim:
 1. A in-orbit space situational awareness system, comprisingmultiple in-orbit host satellites, each host satellite having at leastone space situational awareness enhancement module attached in-orbit orprior to launch, the space situational awareness enhancement modulescomprising at least one of a satellite spatial position sensor, a rangesensor, a navigation sensor, and a proximity sensor for detecting otherobjects in-orbit, and determining at least one of location, speed,acceleration, and orbital trajectory of the other objects, wherein thespace situational awareness enhancement modules communicate to create anin-orbit mesh network between the in-orbit host satellites.
 2. Thein-orbit space situational awareness system of claim 1, wherein thespace situational awareness enhancement modules use at least one ofelectro-optical, RADAR, LIDAR, IR, and RF to determine space objectinformation related to characteristics comprising at least one arelative size, a geometry, and an identification of other space objectsin-orbit.
 3. The in-orbit space situational awareness system of claim 1,wherein the space situational awareness enhancement module is attachedto a first in-orbit host satellite without a direct interface with atleast one of a power system, a control system and a processing system ofthe first in-orbit host satellite.
 4. The in-orbit space situationalawareness system of claim 2, wherein the space situational awarenessenhancement module on a first in-orbit host satellite transmits thespace object information to a ground-based space situational awarenesssystem.
 5. The in-orbit space situational awareness system of claim 4,further comprising a hub-and-spoke space situational awareness meshnetwork further comprising additional space situational awarenessenhancement modules on at least one additional in-orbit host satellitethat transmits additional object information to the ground-based spacesituational awareness system.
 6. The in-orbit space situationalawareness system of claim 5, wherein at least one space situationalawareness enhancement module communicates with other space assets. 7.The in-orbit space situational awareness system of claim 5, wherein theadditional space situational awareness enhancement modules communicatewith one another to create an in-orbit mesh network between the in-orbithost satellites.
 8. The in-orbit space situational awareness system ofclaim 5, wherein at least one of the first in-orbit host satellite andthe other in-orbit host satellites are configured to change a trajectorybased on input from the hub-and-spoke space situational awareness meshnetwork.